Results
2006-19-04: The FAA is adopting a new airworthiness directive (AD) for certain Honeywell COM units and transponders, installed on but not limited to certain transport category airplanes. This AD requires a revision to the Normal Procedures section of the airplane flight manual to advise the flightcrew to check the status of the transponder after changing the air traffic control (ATC) code. This AD also requires replacing certain identification plate(s) with new plate(s), testing certain COM units or transponders as applicable, and corrective action if necessary. For certain airplanes, this AD requires replacing the transponders of certain COM units with new or modified transponders. For certain other airplanes, this AD requires installing a modification into certain transponders. This AD results from the transponder erroneously going into standby mode if the flightcrew takes longer than five seconds when using the rotary knob of the radio management unit to change the ATC code. We are issuing this AD to prevent the transponder of the COM unit from going into standby mode, which could increase the workload on the flightcrew and result in improper functioning of the traffic alert and collision avoidance system.
2021-07-16: The FAA is adopting a new airworthiness directive (AD) for certain Leonardo S.p.a. Model AB412 helicopters. This AD was prompted by a cracked spiral bevel gear. This AD requires a one-time visual inspection and a recurring fluorescent magnetic particle inspection (FMPI) of affected spiral bevel gears for a crack, and depending on the inspection results, removing the spiral bevel gear from service. This AD also prohibits installing an affected spiral bevel gear unless it has recently passed an FMPI. The FAA is issuing this AD to address the unsafe condition on these products.
2018-17-13: We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 620-15 turbofan engines. This AD was prompted by reports of low-pressure compressor (LPC) fan blade retention lug failures. This AD requires reviewing the engine maintenance records and replacing the LPC fan blade with a part eligible for installation if the dry-film lubricant (DFL) treatment limit is exceeded. We are issuing this AD to address the unsafe condition on these products.
2006-19-02: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Airbus Model A300-600 series airplanes. That AD currently requires repetitive eddy current inspections to detect cracks of the outer skin of the fuselage at certain frames, and repair or reinforcement of the structure at the frames, if necessary. That AD also requires eventual reinforcement of the structure at certain frames, which, when accomplished, terminates the repetitive inspections. This new AD requires, for airplanes that were previously reinforced but not repaired in accordance with the existing AD, a one- time inspection for cracking of the fuselage outer skin at frames 28A and 30A above stringer 30, and repair if necessary. This AD results from a report that the previously required actions were not sufficient to correct cracking before the structural reinforcement was installed. We are issuing this AD to prevent such fatigue cracking, which could result in reduced structural integrity, and consequent rapid decompression of the airplane.
2021-08-09: The FAA is adopting a new airworthiness directive (AD) for all Airbus SAS Model A330-323, -342, and -343 airplanes. This AD was prompted by the discovery of an erroneous value in some airplane data files that are used for performance computations in the airplane flight manual (AFM). This AD requires revising the existing AFM and applicable corresponding operational procedures, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2021-08-07: The FAA is adopting a new airworthiness directive (AD) for certain Rockwell Collins, Inc. (Rockwell Collins), GPS-4000S Global Positioning Systems (GPS) installed on airplanes. This AD was prompted by an un-annunciated GPS position error, which could cause a misleading localizer performance with vertical guidance (LPV) glidepath, resulting in controlled flight into terrain (CFIT). This AD requires upgrading the GPS-4000S. The FAA is issuing this AD to address the unsafe condition on these products.
2018-18-12: We are adopting a new airworthiness directive (AD) for Airbus Helicopters Model AS350B, AS350B1, AS350B2, AS350B3, and AS350BA helicopters with a Pall Aerospace Corporation inlet barrier filter (IBF) element. This AD requires revising the Rotorcraft Flight Manual Supplement to [[Page 45546]] prohibit operating a helicopter with an IBF element in wet weather and replacing the IBF element if wet. This AD is prompted by a forced landing after an engine flameout. The actions of this AD are intended to address an unsafe condition on these products.
89-02-06: 89-02-06 AEROSPATIALE: Amendment 39-6114. Applicability: Model ATR42 series airplanes, as listed in Aerospatiale Service Bulletin ATR42-27-0027, Revision 2, dated June 27, 1988, certificated in any category. Compliance: Required as indicated, unless previously accomplished. To prevent loss of rudder control, accomplish the following: A. Within 60 days after the effective date of this AD, install screws and nuts having two separate locking devices in the forward and aft quadrant cable stops in the rudder control system, in accordance with Aerospatiale Service Bulletin ATR42-27-0027, Revision 2, dated June 27, 1988. B. An alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Standardization Branch, ANM-113, FAA, Northwest Mountain Region. NOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Standardization Branch, ANM-113. C. Special flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. All persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Aerospatiale, 316 Route de Bayonne, 31060 Toulouse, Cedex 03, France. These documents may be examined at the FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or at the Seattle Aircraft Certification Office, 9010 East Marginal Way South, Seattle, Washington. This amendment (39-6114, AD 89-02-06) becomes effective February 22, 1989.
2006-19-05: This amendment adopts a new airworthiness directive (AD) for the specified restricted category type-certificated helicopters. The AD requires a review of the helicopter records to determine the Commercial and Government Entity (CAGE) code of the tail rotor (T/R) slider. If the T/R slider is FAA approved or has a certain legible CAGE code, this AD requires no further action. If you cannot determine whether the T/R slider is FAA approved and it has no stamped CAGE code, an illegible stamped CAGE code, or an affected CAGE code, the AD also requires, before further flight and at specified intervals, magnaflux inspecting the T/R slider for a crack. If a crack is found, the AD requires, before further flight, replacing the T/R slider with an airworthy T/R slider. The AD also requires replacing the T/R slider with an airworthy T/R slider on or before accumulating 1,000 hours time-in-service (TIS) or on or before 12 months, whichever occurs first. This amendment is prompted by two accidents attributed to sub-standard T/R sliders that failed during flight. The actions specified by this AD are intended to prevent failure of a T/R slider, loss of T/R control, and subsequent loss of control of the helicopter.
2006-18-17: The FAA is superseding an existing airworthiness directive (AD), which applies to certain Boeing Model 747-400, 747-400D, and 747- 400F series airplanes. The existing AD currently requires reviewing airplane maintenance records; inspecting the yaw damper actuator portion of the upper and lower rudder power control modules (PCMs) for cracking, and replacing the PCMs if necessary; and reporting all airplane maintenance records review and inspection results to the manufacturer. This new AD expands the applicability and discontinues certain requirements of the existing AD. This AD adds repetitive inspections of the PCMs, and replacement of the PCMs if necessary. This AD results from manufacturer findings that the inspections required by the existing AD must be performed at regular intervals. We are issuing this AD to detect and correct cracking in the yaw damper actuator portion of the upper and lower rudder PCMs, which could result in an uncommanded left rudder hardover, consequent increased pilot workload, and possible runway departure upon landing.
2018-18-16: We are superseding Airworthiness Directive (AD) 2018-12-08, which applied to certain Airbus SAS Model A330-200 and -300 series airplanes, and Model A340-212, -213, -312, and -313 airplanes. AD 2018- 12-08 required repetitive inspections of certain fastener holes, and related investigative and corrective actions if necessary. This new AD corrects certain compliance time references. This AD was prompted by a report of cracking at fastener holes located at a certain frame (FR) on the lower shell panel junction. We are issuing this AD to address the unsafe condition on these products.
87-13-11: 87-13-11 FAIRCHILD AIRCRAFT CORPORATION: Amendment 39-5668. Applies to Model SA26-T, SA26-AT, SA226-T, SA226-T(B), SA226-AT, SA226-TC (All serial numbers) except SA226-T(B), S/N T-276, T-283 through T-297, SA226-AT, S/N AT-062E through AT-069 and SA226-TC, S/N TC-247 through TC-279; airplanes certificated in any category. Compliance: Required as indicated, unless already accomplished. To prevent inadvertent landing gear selector movement, accomplish the following: (a) On or before December 1, 1987, accomplish the following: (1) Visually inspect the sides and end of the center pedestal for installation of brackets, holders, or any sort of provision for the storage of maps, charts, and approach charts and, prior to further flight, remove any such devices. (2) Modify the landing gear selector lever in accordance with Fairchild Aircraft Corporation S/B 26-32-30-39, dated February 13, 1987 (for the Model SA26 airplanes), or S/B 226-32-048, revision dated February 13, 1987 (for the Model SA226 airplanes), as applicable. (b) Airplanes may be flown in accordance with FAR 21.197 to a location where this AD may be accomplished. (c) An equivalent means of compliance with this AD may be used if approved by the Manager, Airplane Certification Branch, ASW-150, FAA, Southwest Regional Office, Fort Worth, Texas 76193-0150, Telephone (817) 624-5150. All persons affected by this directive may obtain copies of the documents referred to herein upon request to the Fairchild Aircraft Corporation, P.O. Box 790490, San Antonio, Texas 78279-0490; or may examine the documents referred to herein at FAA, Office of the Regional Counsel, Room 1558, 601 East 12th Street, Kansas City, Missouri 64106. Effective on August 10, 1987.
2006-18-16: We are adopting a new airworthiness directive (AD) for certain Raytheon Aircraft Company Model 390 airplanes. This AD requires you to inspect the spigot bearing, part number (P/N) MS14104-16, for the proper position in the spigot fitting assembly and to install the wing spigot bearing retainer kit, P/N 390-4304-0001. We are issuing this AD to detect spigot bearings that are not positioned flush with the fitting assembly. This condition could result in the spigot bearing becoming disengaged from the fitting assembly, which could cause motion between the wing and the fuselage and degrade the structural integrity of the wing attachment to the fuselage. This could lead to wing separation and loss of control of the airplane.
2000-09-14: This amendment adopts a new airworthiness directive (AD) that is applicable to Rolls-Royce plc RB211-535 series turbofan engines. This AD will require removal from service of suspect radial drive steady bearings with certain serial number prefixes and replacement with serviceable parts. This amendment was prompted by reports of a number of radial drive steady bearing failures from distinct batches of parts. The actions specified by this AD are intended to prevent radial drive steady bearing failure, which could result in an in-flight engine shutdown and smoke and fumes in the cabin.
2018-17-12: We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) GE90-76B, GE90-77B, GE90-85B, GE90-90B, and GE90-94B turbofan engines with full authority digital engine control (FADEC) software, version 9.3.2.4 or earlier, installed. This AD requires upgrading the FADEC software to a software version eligible for installation. This AD was prompted by an ice-crystal icing (ICI) event that caused damage to both engines, a single engine stall, and subsequent engine shutdown. We are issuing this AD to address the unsafe condition on these products.
2005-24-11: The FAA is superseding an existing airworthiness directive (AD) that applies to certain EMBRAER Model EMB-135 and Model EMB-145 series airplanes. The existing AD currently requires repetitive inspections of the spring cartridges of the elevator gust lock system to determine if the lock washer projection correctly fits the slots in the cartridge flange, and corrective action if necessary. The existing AD also provides for optional terminating action for the repetitive inspections for certain airplanes. This AD retains the requirements of the existing AD and adds a requirement for final terminating action for all affected airplanes. This AD results from reports of an improperly fitting lock washer causing the clevis of the spring cartridge in the electromechanical elevator gust lock system to become unscrewed. We are issuing this AD to prevent the unscrewing of the spring cartridge clevis from jamming the elevator, which could lead to reduced controllability of the airplane.
88-01-03: 88-01-03 BOEING: Amendment 39-5810. Applies to Model 757 series airplanes equipped with Rolls Royce RB 211-535C or -535E4 engines, specified in Boeing Alert Service Bulletin 757-71A0026, Revision 1, dated September 24, 1987, certificated in any category. Compliance required within one year after the effective date of this AD, unless previously accomplished. \n\n\tTo minimize the potential for total thrust loss in both engines due to a lightning strike, accomplish the following: \n\n\tA.\tModify engine electrical and electronic control unit wiring in accordance with Boeing Alert Service Bulletin 757-71A0026, Revision 1, dated September 24, 1987, or later FAA-approved revision. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197and 21.199 to operate airplanes to a base for the accomplishment of the modification required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to the Boeing Commercial Airplane Company, P.O. Box 3707, Seattle, Washington, 98124. These documents may be examined at the FAA Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or the Seattle Aircraft Certification Office, 9010 East Marginal Way south, Seattle, Washington. \n\n\tThis amendment becomes effective February 16, 1988.
2006-18-10: The FAA is adopting a new airworthiness directive (AD) for certain Airbus Model A340-541 and -642 airplanes. This AD requires a one-time inspection of the anti-stall valve sleeve of the ram air turbine (RAT) for proper installation, determining the part number of the modification plate on the hydraulic pump of the RAT, and follow-on corrective actions if necessary. This AD results from reports of failure of the anti-stall valve on the hydraulic pump of the RAT during scheduled ground tests. We are issuing this AD to prevent failure of the RAT hydraulic pump to supply adequate pressure to activate the RAT, and consequent loss of the RAT as a source of hydraulic and electrical power in an emergency situation.
2021-06-09: The FAA is adopting a new airworthiness directive (AD) for all Fokker Services B.V. Model F28 Mark 0070 and 0100 airplanes. This AD was prompted by a report indicating that a passenger door opened under residual cabin pressure during taxiing after landing, and following the display of the CAB PRESS CTL alert. This AD requires revising the existing airplane flight manual (AFM) to update the Cabin Pressurization Control Fault procedure, as specified in a European Union Aviation Safety Agency (EASA) AD, which is incorporated by reference. The FAA is issuing this AD to address the unsafe condition on these products.
2006-18-08: The FAA is adopting a new airworthiness directive (AD) for certain aviation tires installed on various transport category airplanes. This AD requires a one-time inspection of the nosewheel tires to determine if they are within a designated serial number range, and replacement if necessary. This AD results from reports of tread separations and tread-area bulges on the nosewheel tires. We are issuing this AD to prevent tread separation from a nosewheel tire during takeoff or landing, which could result in compromised nosewheel steering or ingestion of separated tread by an engine, and consequent reduced controllability of the airplane on the runway or in the air.
2021-04-19: The FAA is adopting a new airworthiness directive (AD) for Bell Textron Inc. (Bell) Model 205B helicopters. This AD was prompted by flight testing and fatigue analysis results. This AD requires reducing the life limit of certain tail rotor (T/R) blades and re- identifying them with a new part number (P/N). The FAA is issuing this AD to address the unsafe condition on these products.
2018-18-06: We are superseding Airworthiness Directive (AD) 2013-02-04 for all Rolls-Royce plc (RR) RB211-Trent 970-84, RB211-Trent 970B-84, RB211-Trent 972-84, RB211-Trent 972B-84, RB211-Trent 977-84, RB211- Trent 977B-84, and RB211-Trent 980-84 turbofan engines. AD 2013-02-04 required on-wing inspections of low-pressure turbine (LPT) disk seal fins and interstage seals when post-flight review indicates Engine Health Monitoring (EHM) vibratory maintenance-alert limits were exceeded in flight. This AD requires additional criteria for the inspection of the stage 2, 3, and 4 LPT disk seal fins and interstage seals and removes the requirement to inspect the stage 5 LPT disk seal fins and interstage seal. This AD was prompted by a Trent 900 engine experiencing increased low-pressure rotor vibration while in flight resulting in an in-flight shutdown (IFSD) and air turnback. We are issuing this AD to address the unsafe condition on these products.
2018-17-11: We are adopting a new airworthiness directive (AD) for certain Linstrandt T30 propane cylinders installed on hot air balloons. This AD results from mandatory continuing airworthiness information (MCAI) issued by the aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as welding defects on the propane cylinder that could result in leaking of liquid propane. We are issuing this AD to require actions to address the unsafe condition on these products.
88-22-10: 88-22-10 BOEING: Amendment 39-6055. Applies to Model 757 series airplanes, as listed in Boeing Service Bulletin 757-26-0016, dated May 5, 1988, certificated in any category. \n\n\tCompliance required within the next 15 months after the effective date of this AD, unless previously accomplished. \n\n\tTo prevent depressurization due to loss of all bleed air inflow following crew action based on an erroneous duct leak indication, accomplish the following: \n\n\tA.\tModify the wing and body duct leak detection system in accordance with Boeing Service Bulletin 757-26-0016, dated May 5, 1988. \n\n\tB.\tAn alternate means of compliance or adjustment of the compliance time, which provides an acceptable level of safety, may be used when approved by the Manager, Seattle Aircraft Certification Office, FAA, Northwest Mountain Region. \n\n\tNOTE: The request should be forwarded through an FAA Principal Maintenance Inspector (PMI), who may add any comments and then send it to the Manager, Seattle Aircraft Certification Office. \n\n\tC.\tSpecial flight permits may be issued in accordance with FAR 21.197 and 21.199 to operate airplanes to a base for the accomplishment of the inspections required by this AD. \n\n\tAll persons affected by this directive who have not already received the appropriate service documents from the manufacturer may obtain copies upon request to Being Commercial Airplanes, P.O. Box 3707, Seattle, Washington 98124. These documents may be examined at FAA, Northwest Mountain Region, 17900 Pacific Highway South, Seattle, Washington, or Seattle Aircraft Certification Office, FAA, Northwest Mountain Region, 9010 East Marginal Way South, Seattle, Washington.\n \n\tThis amendment, 39-6055, becomes effective December 7, 1988.
2006-17-51: This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2006-17-51, sent previously to all known U.S. owners and operators of Agusta S.p.A. (Agusta) Model AB139 helicopters by individual letters. This AD requires, before further flight and at specified intervals, certain visual inspections of each tailpipe assembly for a crack and for overheating. If you find areas of overheating, this AD also requires, before further flight, certain inspections for damage to the surrounding structure, outside of the cowling, and inside of each tailpipe assembly in certain areas. This AD also requires, before further flight, if you find a crack, replacing the tailpipe assembly with an airworthy tailpipe assembly. This AD is prompted by several reports of tailpipe assembly cracks. The actions specified by this AD are intended to prevent a fire due to the structure in the cowling area overheating, separation of a part of a tailpipe assembly, and subsequent loss of control of the helicopter.